Optimization of 10 N Monopropellant High Test Peroxide Thruster for Space Applications

Monopropellant thruster is one of the most propulsion system types developed in space industry. This uses a single type propellant that reacts porous medium catalytic packed bed to generate thrust form hot gases. The last decade, green hydrogen peroxide (H2O2), also known as High Test Peroxide (HTP), thanks its low cost and easy store liquid, used an alternative solution hydrazine which very toxic not environmentally friendly. In current study, monopropellant investigated for application future satellites. A numerical simulation performed using Computational Fluid Dynamics (CFD) software ANSYS Fluent order simulate fluid flow thruster, finite volume method was employed resolving governing equation. Species transport model applied single-phase reaction Eddy Dissipation (EDM) turbulence-chemistry interaction. mathematical approach based on local thermal non-equilibrium (LTNE) describe heat transfer through solid phases consisting identical spherical silver particles. Several simulations allowed optimal design injector, catalyst length diameter nozzle geometry, achieve 10N with at 87.5% concentration.